Remote-controlled launch system for missiles

ABSTRACT

The apparatus of the present invention is employed at an unmanned location to launch a missile by commands received over an R. F. link. The invention apparatus processes these commands and applies them to conduct power to the missile, start its engine, arm the electronics, and ignite a JATO bottle which effects the launch. Each received command is interrelated with signals obtained by monitoring the instantaneous missile tail pipe temperature, engine RPM, generator voltage, and radio control system status. Means are provided for aborting a launch if all prescribed missile operating conditions are not met.

Uited States atom Davis [15] 3,680,749 Aug. 1, 1972 PrimaryExaminer-Stephen C. Bentley Attorney-Edgar J. Brower, Q. Baxter Warnerand [72] Inventor: John S. Davis, Port Hueneme, Calif.

Howard J. Murray, Jr. {73] Assignee: The United States of America asRepresented by the Secretary of the [57] ABSTRACT av y The apparatus ofthe present invention is employed at Flled! J y 1969 an unmannedlocation to launch a missile by com- [21] Appl. No.: 844,017 mandsreceived over an R. F. link. The invention apparatus processes thesecommands and applies them to conduct power to the missile, start itsengine, arm

. t v a fi c n n a t l n [5 8] held of Search g with signals obtained bymonitoring the instantaneous missile tail pipe temperature, engine RPM,generator voltage, and radio control system status. Means are [56]References cued provided for aborting a launch if all prescribed missileUNITED STATES PATENTS operating conditions are not met.

2,866,385 12/1958 Miller ..60/243 3 Claims, 11 Drawing Figures RPM-SENSING UNIT I I4 T IR6E i UNIT l6 TAILPIPE FUEL TARGET RECE'VER883%,;25 CONTROL MISSILE UNIT UNIT IO I2 '8 PRE- STARTER LAUNCH CONTROLX MONITOR UNIT TELEMETRY JB I MONITOR UNIT COMILAND Z'AEE CONTROL UNITmm 1 l EXTERNAL POWER LAUNCH ,38

POWER CONTROL 2 CONTROL SOURCE UNIT UNIT PATENTEUAUI; 1 m2 SHEET 2 BF 9NOmm; 6mm;

FIT

THROTTLE INCREASE DECREASE PATENTEDAUB 11972 3580749 saw u 0F 9 1 LTHROTTLE E I 'LO K1067 4 SEC DELAY KIOI 70 SEC DELAY M U LT VIBRATOR 60SEC DELAY TKIOOZ ril KIOOI 30 SEC DELAY 1 y POWER KIOO3 PATENTED AUG 1I972 30 SEC DELAY SHEET 8 BF 9 4 SEC DELAY T KI706 OJ KIIOI T K330i FUELCONTROL UNIT Fig.7

PATENTEDAUB 1 I912 SHEET 9 (IF 9 POWER I K1807 70 SEC.

DELAY (LOW THRUST) 5 SEC DELAY DC POWER POWER COMMAND C 4 D llll ll 0 \lm K m F E M E m K 9 R O E I: m m K R A C 8 0 Q1. m. K NW.- R C E0 D 0 WPP 9 POWER K80! INTERLOCK UNIT REMOTE-CONTROLLED LAUNCH SYSTEM FORMISSHJES STATEMENT OF GOVERNMENT INTEREST The invention described hereinmay be manufactured and used by or for the Government of the UnitedStates of America for governmental purposes without the payment of anyroyalties thereon or therefore.

BACKGROUND OF THE INVENTION At the present time many missiles are beinglaunched by personnel located in the immediate vicinity of the launchingoperation. This constitutes a hazard to such personnel in the event of amalfunction of such nature as to cause the missile to blow up orotherwise destruct before it has traveled any appreciable distance.Although remote-controlled systems have been tried previously, they havefrequently failed to take into consideration the instantaneous operatingstatus of each missile component or sub-assembly at the time it is to besequenced into the launch program. Furthermore, provisions for abortingor terminating the launch after it has been initiated have often beenomitted resulting in unnecessary firings with consequent waste of moneyand equipment.

SUMMARY OF THE INVENTION The present invention is directed to a missilelaunchcontrol unit or assembly which responds to commands received overan RF. link to initiate a series of launchcontrol events which may(according to the particular missile with which the invention apparatusis used) include engine starting, power transfer, control systemcheck-out, and ignition of the firing means. When the invention systemis employed in conjunction with a missile equipped with a JATO unit, thecommands so received may incorporate some or all of the following: (1)external power on: (2) external power off; (3) engine start; (4) JATOarm; (5) .lATO fire; (6) engine shutdown; (7) system reset. The externalpower-on command applies external power to the missile. The externalpower-off command removes external power from the missile. Theengine-start command activates the throttle system, fuel system, starterand igniter system. When these systems are activated, they will startand run the missile engine, monitoring the engines tail pipe temperatureand RPM. The engine RPM will increase to a preset launch RPM andtransfer to internal generator power. The JATO-arm command activates theJATO fire-command system so it may receive and process a JATO firecommand. The .IATO fire command ignites the JATO bottle which launchesthe missile. The engine-shut-down command will safely shut down themissile engine and safe the JATO firecommand system. After the enginehas completely stopped rotating the starter system is reactivated towindmill the engine to cool the engine tail pipe to a safe temperature.The reset command resets the Launch Control Unit so that a restart maybe accomplished after a shut-down command has been received.

OBJECTS OF THE INVENTION One object of the present invention is toprovide a remote-controlled launch system for missiles.

Another object of the invention is to provide a system for launching amissile through a predetermined sequence of commands transmitted to themissile over an RF. link.

A further object of the invention is to launch a missile by remotecontrol while at the same time providing means for aborting the launchat any time if all prescribed missile operating conditions are not met.

Other objects, advantages, and novel features of the invention willbecome apparent from the following detailed description of the inventionwhen considered in conjunction with the accompanying drawings.

BRIEF DESCRIPTION OF THE DRAWINGS FIG. 1 is a block diagram of aremote-controlled missile launching system designed in accordance with apreferred embodiment of the present invention;

FIG. 2 is a schematic electrical diagram of the power control unit ofFIG. 1;

FIG. 3 is a schematic electrical diagram of the temperature-sensing unitof FIG. 1;

FIG. 4 is a schematic electrical diagram of the RPM- sensing unit ofFIG. 1;

FIG. 5 is a schematic electrical diagram of the throttle control unit ofFIG. 1;

FIG. 6 is a schematic electrical diagram of the starter control unit ofFIG. 1;

FIG. 7 is a schematic electrical diagram of the fuel control unit ofFIG. 1;

FIG. 8 is a schematic electrical diagram of the launch control commandunit of FIG. 1;

FIG. 9 is a schematic electrical diagram of the monitor tmit of FIG. 1;

FIG. 10 is a schematic electrical diagram of an interlock system to beemployed in conjunction with the system of FIG. 1; and

FIG. 11 is a schematic electrical diagram of a manual check-out systemwhich may be employed in conjunction with the arrangement of FIG. 8.

DESCRIPTION OF THE PREFERRED EMBODIMENT The remote-controlled launchsystem of the present disclosure is, in a preferred embodiment, composedof the sub-assemblies or units illustrated in FIG. 1 of the drawings.The system is designed to launch a missile 10 by commands originating ata remote point and picked up by a receiver 12. One arrangement which hasproven to be successful in practice is intended to launch a targetmissile (such, for example, as that known as the Firebee or BQM-34A)from a surface craft on which the invention apparatus is installed.However, the concept herein set forth is obviously adaptable to manydifferent types of missiles which would otherwise present a hazard topersonnel in the immediate vicinity of a launch operation.

The basic units (or sub-assemblies) of the invention embodiment setforth in FIG. 1 of the drawings include a unit 14 for sensing the tailpipe temperature of the missile 10, a cooling unit 16, a pre-launchmonitor 18, a shut-down unit 20, a command control unit 22, a powercontrol unit 24, an RPM sensing unit 26, a throttle control unit 28, afuel control unit 30, a starter control unit 32, a monitor 34, apre-launch control unit 36, a launch control unit 38, and a telemeteringunit 40. The details of certain of these units will be set forthhereinafter in connection with a description of FIGS. 2 through 11 ofthe drawings.

In designing the system of the present concept, it was found thatalthough it was desirable to break up the various functions of thesystem along the lines set forth in FIG. 1 of the drawings, neverthelesssuch a physical separation of parts did not lend itself to convenientcheck-out or troubleshooting in the event of a malfunction.Consequently, it was decided to assemble the various components of thesystem into modules in the form of circuit boards which could readily bewithdrawn from the system for repair and/or replacement of any or allcomponents wired thereon. However, since the manner in which theindividual elements of each unit or sub-system are grouped into modulesis not necessarily representative of the function of any particularmodule, the following description will be based primarily upon theinterrelationship of the elements making up each unit of FIG. 1. In sodoing, however, it is considered necessary to make reference to themodular status of certain parts, especially when such parts are carriedon a single module but are included in more than one of thesub-assemblies of FIG. 1. The following table lists by number of modules(designated M) into which all of the components making up the units ofFIG. 1 have been assembled, although such grouping is impracticable (andunnecessary) to illustrate in the drawings:

M1 Fuel, throttle, and starter control module M2 Throttle pulser M3 Mainfuel control M4 200 temperature detector M5 650 and 760 temperaturedetector M6 1,000 temperature detector M7 Temperature amplifier M8 90%RPM detector M9 10% RPM detector M10 Engine stabilization and cooling M11 33% RPM detector M12 65% RPM detector M13 85% RPM detector M14 88% RPMdetector M15 Interlock M16 Command M17 Miscellaneous M18 Pre-startmonitor M19 Pre-launch monitor M20 Remote monitor M22 Carrier monitorM24 Automatic/manual selector M27 Power control relays M28 Regulatedpower supplies M29 100 detector M30 0% RPM detector M32 Over-voltagedetector M33 Power control To aid in an understanding of theinterrelationship between the units of FIG. 1 and the modules of theforegoing table, the various components of each unit have beendesignated by the module on which they are carried. For example,component K3303 of FIG. 2 forms part of module M33, while component K801of FIG. 10 forms part of module M8. In the following description, bothunits and modules will be referred to as may be appropriate under thecircumstances. The prefix K is employed throughout to designate a relay.

P WER CONTROL UNIT The power control unit of FIG. 2 consists of modulesM27, M28, M33, terminal strips TB101, TB102, TB103, TB201, TB202 and thestarter power relay K13. Module M27 contains three main power relayswhich direct power to the automatic system, manual system, and to themissile. Module M33 controls the activation of module M27. Module M28contains two regulated power supplies which provide a positive 18- VDCand a negative l2-VDC. TB101 is a ZOO-amp shunt which all DC inputcurrent is routed through. Terminal strip TB 102 and TB103 distribute DCcurrent throughout the system. Terminal strip TB201 and TB202 are groundbuses. Starter power relay K13 controls the heavy DC current required bythe starter.

Three supply voltages are supplied J 101, J102, and J 104. Each supplyvoltage will be discussed separately. A 30-vo1t DC source, capable ofsupplying a lOO-amp surge for 5 seconds and 50 amps continuous, isapplied to connector I101. Power is directed from J 101 to TB101. TB101is a ZOO-amp shunt which operates an ammeter (not shown). TB101furnishes DC current to contacts on relays K2701, K2702, K2703, K3303and the master power switch. When the master power is actuated to themanual position, relay K2701 is energized. Relay K2701 furnishes DCcurrent to a manual control to be described below. When the master powerswitch is actuated to the automatic position, DC current is routedthrough contacts of K2204 and energizes relay K3303. K3303 directs DCcurrent to TB103 and the l8-VDC regulated power supply of module M28.K3303 also applies control voltage to relay K3302 which has a 2-secondenergizing delay. When relay K3302 energizes, control voltage is appliedto relay K2703. K2703 supplies DC current to TB102. When commanded,relay K1602 energizes to furnish control voltage through the contacts ofrelay K2401 to the external power relay K2701. Relay K2701 furnishes DCpower to the missile. Two external 1 l5-VAC, -cycle, l-arnp sources areused. One primary and one is secondary. They are routed through Jl04 torelay K2704. Relay K2704 supplies the ll5-VAC source to transformer T-l.Transformer T-l steps the l l5-VAC down to 26 VAC and supplies the 26VAC to relay contacts of K3303. When K3303 is energized, 26 VAC issupplied to the regulated negative l2-VDC power supply located on M28.Receptacle J102 requires an input source of 30 VDC capable of a1,000-amp surge for 3 seconds and a sustained 600-amp capability for 30seconds. J 102 supplies DC current to relay K13. Relay K13, whenenergized, supplies DC current for the missile starter motor. TB102,TB103 and the positive 18 VDC and negative 12 VDC of module M28, supplythe current to all systems.

ENGINE CONTROL SYSTEM The engine control system is divided into fivesubsystems or units, as follows:

a. the tail pipe temperature sensing unit (FIG. 3)

b. the RPM sensing unit (FIG. 4)

c. the throttle control unit (FIG. 5)

d. the starter control unit (FIG. 6)

e. the fuel control unit (FIG. 7) These will now be described in detail:

a. Tail pipe temperature sensing unit The tail pipe temperature sensingunit of FIG. 3 consists of four temperature detectors and twoamplifiers. The temperature detectors are modules M4, M5, M6, and M29.The two temperature amplifiers are located on M7. The two temperatureamplifiers are connected to the missile engine tail pipe thermocouples.Engine thermocouples produce a DC voltage which is proportional to theengine tail pipe temperature. The DC voltage level produced by thethermocouple is an extremely low voltage and requires amplification. Thetwo amplifiers located on M7 provide this needed amplification. Of thetwo amplifiers, one amplifies the voltage level corresponding to to 600centigrade. The second amplifier, amplifies the voltage levelcorresponding to 400 to l,000. The 0 to 600 amplifier provides atemperature signal to modules M4 and M29. The 400 to l,000 amplifierprovides a temperature signal for modules M5 and M6. Module M4 isadjusted to detect a temperature of 200 and energizes K401. M29 detectsa temperature of 100 and energizes K2901. Module M5 is adjusted todetect two temperatures, 650 and 760. When a temperature of 760 isdetected, relay K501 will energize. K501 will remain energized until thetemperature reduces to 650 at which time K501 will de-energize. ModuleM6 detects a temperature of 1,000 and energizes relay K601. The enginetail pipe thermocouples are connected to a temperature indicator (notshown). The input to module M7 is also connected to the enginethermocouples. The output of M7 is connected to the four temperaturedetectors, M4, M5, M6 and M29.

b. RPM sensing unit The engine RPM sensing unit of FIG. 4 consists ofseven RPM detectors. The seven RPM detectors are modules M8, M9, M11,M12, M13, M14 and M30. The RPM modules are coupled to the output of themissile engine tachometer. The engine tachometer produces an AC voltageand frequency which is proportional to the engine RPM. The RPM moduledetectors are adjusted to detect specific frequencies. The following isa list of RPM detectors and the adjustment in engine RPM percentages:

a. M8 90% b. M9 10% 0. M11 33% d. M12 65% e. M13 85% f. M14 88% g. M300% RPM percentages, and the relays which they operate:

Module Percentages Relay M8 90% K801 M9 10% K901 M11 33% K1101 M12 65%K1201 M13 85% K1301 M14 88% K1401 M30 0% K3002 c. Throttle control unitThe throttle control unit of FIG. 5 consists of modules M2, M10, part ofM1, and the relay contacts of M4, M5, M8, M9, M12, M13, M14, M16, andM17. When the master power switch is activated to the automaticposition, the -second delay timer located on module M1 is activated. The70-second timer applies a decrease thrust signal to the throttle servo.This function assures that the missile throttle is fully retarded prior.to starting the engine. After a 70-second delay, a signal is sent fromthe timer to the start interlock circuit. When the start command isapplied, DC current is applied to the throttle 4-second timer located onM1 to advance the throttle. When engine RPM reaches 10 percent and thetail pipe temperature reaches 200, DC current is applied to the throttlepulser located on Module M2. The throttle pulser applies DC current toadvance the throttle at one second intervals. The throttle continues toadvance with pulses until the engine RPM reaches 65 percent RPM. 1n theevent the tail pipe temperature exceeds 760, the throttle will cease toincrease until the temperature reduces below 650. When the temperaturedecreases, the throttle will resume pulsing. When the engine RPM reaches65 percent, the throttle will stop advancing for 30 second. This30-second period is to allow the engine to stabilize. After the30-second engine stabilization period, a continuous DC current isapplied to advance the throttle until the engine RPM has reaches 85percent. The continuous throttle action, rather than pulsing thethrottle, is to allow the engine to advance as quickly as possiblethrough its critical RPM breathing range of 70 to percent RPM. Atpercent RPM, the throttle is again pulsed until the engine RPM reaches89 percent launch RPM. When the shut-down system is activated thethrottle is returned to decrease thrust. The throttle shut down systemis activated under two conditions: (1) above 65 percent RPM and (2 below65 percent RPM. If the engine RPM is below 65 percent and a shut down isinitiate, a continuous DC current is applied to the decrease thrust. Ifthe engine RPM is above 65 percent a pulsing DC current is applied tothe decrease thrust. When the engine RPM reduces to 65 percent thethrottle is interrupted for 60 seconds. This 60- second period is toallow the engine tail pipe temperature to cool. After the 60-secor1ddelay, the throttle system is reactivated in the same manner as when ashut down is initiated below 65 percent engine RPM. When the masterpower switch is activated to the automatic position, DC current isapplied to K1602, K1605, K1003, K1301 and K1704. DC current is routedthrough the contacts of K1602 to K101 and the 70- second timer. Thecontacts of K101 apply current to the coil of K1704. K1704 appliescurrent through its contacts to the missile decrease thrust throttle.When the starter system is activated, K1602 is energized. When K1602 isenergized, DC current is removed from K101 and applied to K106 and a4-second timer. Current is routed through the contacts of K106 to thecoil of K1702. When K1702 is energized, current is applied to missileincrease thrust throttle. K106 keeps K1702 energized until the 4-secondtimer energizes K106. After the engine starts and engine RPM reaches 10percent, K90l is energized. Current is routed from the contacts of K1605through K1201 and through K901 to K401. When the tail pipe temperaturereaches 200, K401 energizes and routes current through K501 to K201 andthe multivibrator which activates the coil of K201. The multivibratorswitches K201 such that it is I second on and 1.5 seconds off. When K201is energized, current is applied to K1702 through K202 to increase thethrottle position. K501 is controlled by a tail pipe temperature of 650to 750. When K501 is energized, the current to K201 is interrupted andremains so until K501 de-energizes. At 65 percent RPM, K1201 energizes.When K1201 energizes, current is removed from K901 which removes currentfrom the throttle pulser. At the same time current is removed from K901,current is applied to K1001 and K1003. After a 30-second delay, K1001energizes and applies current to K201 coil through K1301. Current isalso routed to the contacts of K201 through K501. K201 remains energizeduntil K1301 energizes at 85 percent interrupting the current from K1001.When K1301 energizes, current is applied to K1401 and K801-Current fromK1401 is applied to K201 and the throttle pulser through K501. At 85percent RPM, K1401 energizes, removing current from K201. If the engineRPM exceeds 90 percent, K801 will energize and apply current to K201 andthe throttle pulser. Current is also applied to K202. When K202 isenergized, current is directed to K1704 instead of K1702. K1704 routescurrent to decrease throttle. K1401 and K801 will position the enginethrottle so as to position an engine RPM above 88 percent and below 90percent. When a shut-down command is activated, K1605 will energize,removing current to the upper sets of contacts and placing it on thelower set of contacts of K1201. If the engine RPM has not yet reached 65percent, current will be routed through the normally closed contacts ofK1003, and the coil of K1704, to decrease thrust. If engine RPM hasexceeded 65 percent RPM, K1201 will be energized and current will berouted to K202 coil, the throttle pulser and to the contacts of K201.This will decrease the engine throttle with pulses. When the RPM reducesto 65 percent RPM, K1201 will de-energize, removing current from K202,K201 and the throttle pulser and directing current to K1003. When theengine RPM was above 65 percent, K1003 energized and locked closed thecontacts of K1002. When current is applied to K1003, it is directed to a60-second timer of K1002. After 60 seconds, K1002 energizes and releasesthe locking current of K1003, de-energizing K1003. When K1003de-energizes current is directed to K1704 decreasing engine RPM,.

d. Starter control unit The starter control unit of FIG. 6 consists ofmodule M30, parts of M1, and the relay contacts of M6, M11, M15, M16,and M29. Also contained in the starter unit is relay K13. Relay K13controls the heavy current required by the missile starter. When a startcommand is initiated, current is directed through the start interlocksystem and energizes the start command relay. When the start commandrelay is energized, the missile throttle is advanced for 4 seconds.After the 4-second throttle, the missile fuel pump is activated for 4seconds. When the fuel pump turns off after 4 seconds, the starter powerrelay is energized and power is applied to the missile starter. Thestarter continues to rotate until the engine RPM reaches 33 percent. At33 percent RPM, the starter power relay is de-energized. In the eventthe engine fails to start and engine RPM fails to reach 33 percent, atimer limits the maximum time that the starter will be energized. Thetimer is adjusted for a maximum time of 30 seconds. If, during thestarting of the engine, the tailpipe temperature reaches 1,000, thestarter power relay will de-energize allowing the engine to be shutdown. The starter control system also contains a windmill circuit forcooling the engine tail pipe. This system is activated at any time thetail pipe temperature is in excess of and the engine RPM is at 0percent. When this condition exists, the starter power relay K13 willenergize and remain so for 10 seconds. At the end of 10 seconds K13 willde-energize and allow the engine to stop. When 0 percent RPM is reachedagain, and the temperature is still in excess of 100, the coolingcycle'will repeat itself. These 10 second cooling cycles continue untilthetail pipe temperature reduces below 100. When the master power switchis placed in the automatic position, DC power is applied to the contactsof K1502, K1605, K2901 and K3002. When a start command is initiated, DCpower is routed through the contacts of the starter interlock relayK1502 to the start command relay K1602. When K1602 energizes, it locksclosed with DC power from K1605 through K1101 and K601. DC power is alsorouted from K1602 to K102. After a 4-second delay K102 energizes andapplies DC power to K103 through the contacts of K106. After another4-second delay K103 energizes and applies DC power to K13 through thecontacts of K105 and K104. K13 applies DC power to the BQM-34A starter.When the engine RPM increases to 33 percent, K1101 releases K1602locking power. When K1602 releases, K13 de-energizes releasing the powerfrom the missile starter. In the event the tail pipe temperatureincreases to 1,000, K601 energizes and will also release K1602. If theengine fails to start or the engine RPM does not reach 33 percent within30 seconds after K13 energizes, K104 will energize interrupting thepower to K13 coil. If a shut-down command is initiated while the starteris energized, the power will be interrupted to K1602. During thewindmill cycle K2901 is activated whenever the tail pipe temperature isin excess of 100. Power is routed through K2901 to K3001. When theengine RPM reduces to 0 percent, K3001 energizes, applying DC power toenergize K3002. When K3002 energizes, it locks closed through K3003 andalso applies power to K13 through K104. As the engine begins to rotateK3001 de-energizes breaking the energizing power source to K3002 coil,leaving only the locking power through the contacts of K3003. After thetimer (10 seconds) runs out, K3003 energizes, releasing the lockingpower to K3002. When K3002 de-energizes, power is removed from K13releasing power from the missile starter. This complete cycle continuesuntil the tail pipe temperature reduces below 100 and releases K2901.

e. Fuel control unit The fuel control unit of FIG. 7 consists of moduleM3, part of M1, M17, M33, and the relay contacts of M6, M10, M11, andM16. The fuel system is activated by the start command system. When astart command has been initiated, the throttle is advanced for 4seconds. At the end of the 4-second throttle advance, the fuel pump,located in the missile is activated for 4 seconds. This 4 seconds offuel time is to pressurize the fuel system to assure an enginelight-off. At the end of the 4 seconds of fuel, the engine starter isenergized. At the same time that the starter is activated, DC power isapplied to the missile ignitor and start fuel valve. 2.2 seconds afterthe starter has been activated, the fuel pump is again activated andlocks on. When a shut down command is initiated, the fuel pump isde-activated shutting the engine fuel off. If the engine tail pipetemperature reaches l,000, the fuel pump will also be shut off. During anormal engine shut down when the missile has been on internal power, thefuel pump will remain on until the engine RPM reduces to a point wherethe missile low voltage relay cuts off the internal power. When themaster power switch is placed in the automatic position, DC power isapplied to the contacts of K1602 through K1605, K1101 and K601. Power isalso applied to the contacts of K1701, K301 and K3301. When the startcommand is initiated, K1602 energizes applying DC power to K102. Fourseconds after power is applied to K102, K102 energizes, applying powerto the coil of K105 through K106 and K103. When K105 energizes, power isapplied to the coil of K1701, energizing K1701. When K1701 energizes,power is applied to the fuel pump. Relay K105 remains energized untilthe 4-second timer of K103 activates. When K103 energizes, K105de-energizes removing power from K1701, turning the fuel pump off. WhenK103 energizes and K105 de-energizes, power is applied to the coil ofK1706 through K104 and K1101. When K1706 energizes, power is applied toK301 timer. 2.2 seconds after power has been applied to K301 timer K301energizes and locks on. K301 applies power to K1701 which activates thefuel pump. When K1706 energizes, power is also applied to K3301. K3301applies power to the missile igniter and the start-fuel valve. When theengine reaches 33 percent RPM, K1101 energizes removing power fromK1706. When K1706 de-energizes, K3301 will de-energize removing powerfrom the missile igniter and startfuel valve. A shut-down command(K1605) or over temperature of l,0() (K601) will remove power fromK1602. When power is removed from K1602, all power is removed from thefuel control circuit except K301 which may be locked in. This circuit isinterrupted by K1004 when K1605 energizes (note FIG. 5).

COMMAND CONTROL SYSTEM The command control system is divided into threesub-systems or units, as follows:

a. launch control command unit (FIG. 8)

b. monitor (FIG. 9)

c. interlock unit (FIG. 10) These will now be described in detail:

a. Launch control command unit The launch control command unit of FIG. 8consists of modules M16, M22 and M34. These modules receive and processall command signals transmitted to the receiver 12 of FIG. 1. There area total of seven (7) commands which may be received by the commandsystem: (1) external power on; (2) external power off; (3) engine start;(4) arm; (5) launch; (6) shut down; (7) reset. Also included in thissystem is a launch control command carrier monitor circuit. The carriermonitor circuit provides a fail-safe condition in the event there is afailure in the command control R.F. carrier link. The external power-oncommand places external power on the missile. The external power-offcommand removes external power. The engine-start command activates themissile engine starter, fuel, throttle, and igniter system. Thesesystems, when activated, will start and run the missile engine. The armcommand arms the firing circuit to the JATO igniter. The launch commandignites the JATO igniter. The shut-down command shuts the engine off andsafes the system to prevent an engine start. The reset command resetsthe shut-down system so an engine-start command may be processed. Thelaunch control command carrier monitor circuit monitors the commandcontrol R.F. carrier. In the event there is a loss of an R.F. carrierfor seconds or more, the carrier monitor circuit will activate theshut-down system.

All commands are received through I 103. The external power-on commandis received through pin D of J 103 and routed to the coil of K1602. WhenK1602 is energized it will remain energized with power from thenormally-closed contacts of K1601. With K1602 energized, DC power isrouted through K1705, K2401 and to the coil of K2701. K2701 appliesexternal power to the ROM-34A. The external power off command isreceived through pin C of J 103 and routed to the coil of K1601. WhenK1601 is energized, K1602 will de-energize and remove external powerfrom the missile. The engine-start command is received through pin J ofJ 103 and is routed through the contacts of K301 and K1502 to the coilof K1603. When K1603 is energized, it activates the engine start system.The arm command is received through pin A of J 103 and power is routedthrough the contacts of K1503 and K1504 to the coil of K3401. When K3401is energized it remains energized by power from K1605. The launchcommand is received through pin B of J 103 and power is routed thecontacts of K1505 to the coil of K3402. When K3402 is energized, theshort circuit between the two JATO igniter wires are removed and poweris applied to one lead and a ground is applied to the other. Thiscompletes the circuit for the JATO igniter. The shutdown command isreceived through pin E of J 103 and power is routed to the coil ofK1605. At any time K1605 is energized, a system shut-down will be ineffect which safes the console and prevents the missile engine frombeing started and the JATO igniter from being ignited. The reset commandis received through pin G of J 103 and power is routed through twopaths. If the engine has not yet been started, power will be routedthrough the contacts of K2205 and to the coil of K2204. When K2204 isenergized, power is interrupted to the coil of K3303 which removes powerfrom the entire system thereby resetting all functions. If the enginehas been started, K2205 will be energized and power will then be routedthrough the contacts of the 10- minute timer relay K2203 and K1605 tothe coil of K2204. The reason for the timer is, if the engine has beenrunning and a shut-down is initiated, there will be ample time for theengine to shut down and for the tail pipe temperature to cool off priorto attempting a restart. The carrier monitor signal is received throughpin F of J 103 and power is routed to the coil of K2201. Whenever thereis a failure of the RF. carrier, the power to K2201 is removedde-energizing K2201. When K2201 is de-energized, power is routed to thetimer of K2202. If power remains on the timer for 60 seconds or moreK2202 will energize allowing power to be routed to the coil of K1605initiating a shut-down.

b. Monitor The command control monitor of FIG. 9 consists of module M20and part of M18. During a remote launch, it is necessary to assure thatthe missile command control system is functioning properly. This isaccomplished by remotely commanding a missile climb, dive, right turn,and left turn. As these commands are received by the missile, module M20monitors each function as it occurs and locks a relay closed. After allfour (4) commands have been detected, a signal is provided to theinterlock system to complete that part of the launch interlock circuit.Also included in the missile command control monitor system is a commandcontrol carrier monitor. This monitor is located on M18. The carriermonitor will prevent an engine-start command from being received andwill initiate the shut-down system if the engine has been startedwhenever there is a failure in the missile command RF link for 5 secondsor more.

A dive command energizes K2004, a climb command energizes K2003, a leftturn energizes K2002, and a right turn energizes K2001. When theserelays are energized, they will complete a series circuit and route DCpower to the coil of K1504. Relay K1504 is part of the launch interlocksystem. Whenever there is a loss of command control R.F. carrier, relayK1804 will de-energize, allowing DC power to be routed to K1809. IfK1804 remains de-energized for five (5) seconds or more K1809 willenergize, interrupting the start command circuit. If the missile enginehas been started, DC power will be routed through the contacts of K1101and to the coil of K1604, initiating a shut down.

c. Interlock unit The command interlock unit of FIG. assures thatcertain conditions are met prior to allowing commands to be received bythe launch control command system. The command interlock system consistsof modules M15, M18 and M19. Prior to allowing an engine-start commandto be received, there must be external power on the missile, a commandcarrier must be present, a launch control command carrier must bepresent, the missile autopilot must be initiated, and the 70-secondthrottle decrease thrust timer must be timed out. With these conditionsbeing met, a start command may be received and processed. Prior toallowing the arm command to be received, the engine RPM must be betweenthe limits of 88 and 90 percent, the missile must be on internal power,and the missile must have received all four remote checks (climb, dive,left turn and right turn). The arm command may then be received. Thelaunch command may be received at any time after an arm command has beenreceived.

The pre-start monitor completes the circuit for the engine-start commandto be received by the command system. When K1801 is energized by themissile external power, DC power is routed through the contacts of K1801to K1802. The autopilot bus energizes K1802 and DC power is routed toK1809. K1809 is the command control carrier 5-second timer. As long asthe command control carrier does not remain off for 5 seconds or more,DC power is routed through K1809 to K1807. K1807 is energized by thethrottle second decrease thrust timer. This completes the engine startinterlock circuit and DC power is directed to the coil of K1502. WhenK1502 is energized, the engine start command may be received. The arminterlock consists of relays K1909, K1908, K1504 and K1503. K1908 isenergized by the internal power and routes DC power to K1909. K1909 isenergized by K801 and K1401. When the engine RPM is above 88 percent andbelow 90 percent, K801 and K1401 are energized and route DC power toK1909. With K1909 energized DC power is routed to the contacts of K1504.The command control monitor system provides DC power to energize thecoil of K1504. When K1504 is energized DC power is routed to the coil ofK1503. With K1504 and K1503 energized, the arm command may be receivedby the command system. When the arm command is received, K1604 isenergized and allows DC power to be routed through its contacts and thecontacts of K1504 to the coil of K1505. When K1505 is energized, itallows the launch command to be received.

AUTOMATIC MANUAL CONTROL The automatic manual control unit of FIG. 11provides a set of switches to manually command the same functions as thecommand control carrier system. There is also a launch control commandcarrier test switch. The switches are provided so that a complete systemtest may be accomplished without the need for an RF. transmitter andtone generator.

There is a total of 8 switches in this section of M31. They are asfollows: l external power on; (2) external power off; (3) engine start;(4) arm; (5) launch; (6) shut down; (7) reset; and (8) carrier test. Allof these switches except the carrier test parallel the functions of thecommand receiver which enters the console at J 103. The carrier testfunction energizes relay K3101. K3101 is a 12-VDC relay with a 330-ohm2-watt resistor in series with the ground lead of the relay coil. WhenK3101 is momentarily energized, it will remain energized by DC powerthrough its own contacts. The other contacts provide a DC signal whichparallels the carrier signal at J 103. Once K3101 is energized, it willremain so until the external power-on command is given either remotelyor manually. When external power-on is commanded, K3101 will release.

I claim:

1. In a system designed to launch a JATO-assisted missile from anunmanned area through the medium of commands in the form of electricalsignals transmitted from a remote point, the combination of:

means in the vicinity of, but external to, said missile for receivingsaid commands;

means responsive to the reception of a particular command by saidfirst-mentioned means to electrically connect the engine of said missileto a source of external power;

means responsive to the reception of a subsequent particular command bysaid first-mentioned means to start the engine of said missile, saidmeans including means for applying a decrease thrust to the throttle fora predetermined period of time prior to starting, and means for pulsingthe throttle advance at one second intervals between the approximatemaximum RPM limits of to 65 percent and 85 to 90 percent;

means responsive to the reception of a still subsequent particularcommand by said first-mentioned means to arm the said JATO unit;

means responsive to the reception of a still subsequent particularcommand by said first-mentioned means to ignite the said JATO unit andthus effect a launch of said missile;

means for monitoring the tail pipe temperature of said missile;

means for monitoring the speed of the said missile engine; and

means for aborting a missile launch at any point in the said commandsequence if either or both the missile tail pipe temperature and enginespeed as ascertained by said monitoring means lies outside predeterminedlimits.

2. The combination of claim 1 in which the means for monitoring thespeed of the missile engine includes a tachometer designed to produce anAC output the frequency of which is proportional to engine speed, and aplurality of detectors connected to receive the output of saidtachometer, each of said detectors being responsive only to apredetermined engine speed as represented by the frequency of the ACinput thereto, each of said detectors being designed to respond to anengine speed difi'erent from the speeds to which all of the remainingdetectors are responsive.

3. The combination of claim 2 in which said missile is equipped with aninternal generator, and means for switching from said source of externalpower to internal generator power when the speed of said engine reachesa predetermined level as sensed by the particular one of said pluralityof detectors which is responsive to engine speed at such level.

1. In a system designed to launch a JATO-assisted missile from anunmanned area through the medium of commands in the form of electricalsignals transmitted from a remote point, the combination of: means inthe vicinity of, but external to, said missile for receiving saidcommands; means responsive to the reception of a particular command bysaid first-mentioned means to electrically connect the engine of saidmissile to a source of external power; means responsive to the receptionof a subsequent particular command by said first-mentioned means tostart the engine of said missile, said means including means forapplying a decrease thrust to the throttle for a predetermined period oftime prior to starting, and means for pulsing the throttle advance atone second intervals between the approximate maximum RPM limits of 10 to65 percent and 85 to 90 percent; means responsive to the reception of astill subsequent particular command by said first-mentioned means to armthe said JATO unit; means responsive to the reception of a stillsubsequent particular command by said first-mentioned means to ignitethe said JATO unit and thus effect a launch of said missile; means formonitoring the tail pipe temperature of said missile; means formonitoring the speed of the said missile engine; and means for abortinga missile launch at any point in the said command sequence if either orboth the missile tail pipe temperature and engine speed as ascertainedby said monitoring means lies outside predetermined limits.
 2. Thecombination of claim 1 in which the means for monitoring the speed ofthe missile engine includes a tachometer designed to produce an ACoutput the frequency of which is proportional to engine speed, and aplurality of detectors connected to receive the output of saidtachometer, each of said detectors being responsive only to apredetermined engine speed as represented by the frequency of the ACinput thereto, each of said detectors being designed to respond to anengine speed different from the speeds to which all of the remainingdetectors are responsive.
 3. The combination of claim 2 in which saidmissile is equipped with an internal generator, and means for switchingfrom said source of external power to internal generator power when thespeed of said engine reaches a predetermined level as sensed by theparticular one of said plurality of detectors which is responsive toengine speed at such level.